【作者】 张泽；

【导师】 韦常柱；

【作者基本信息】 哈尔滨工业大学 ， 航天工程（专业学位）， 2020， 硕士

【摘要】 空间非合作目标的交会对接技术在空间环境清理、提高卫星利用效率以及军事战略方面都有巨大的潜在价值,近年来一直受到大量学者的关注和研究。本文针对空间非合作目标近距离的接近绕飞轨迹设计和姿态控制技术进行研究,给出各段的设计方法并给出相应的算例和仿真分析。首先定义相关的坐标系及相应的转换关系,建立飞行动力学模型及摄动模型,并推导了航天器相对轨道动力学模型,为后面的算法设计提供理论基础。在近程导引段,考虑到非合作目标轨道信息测量不精确的问题,将近程导引段按照相对距离划分为两个阶段。在相对距离较远时采用基于C-W状态方程的脉冲制导进行初步接近,推导并给出了双脉冲和多脉冲轨道转移的设计方法;在相对距离较近时采用视线制导,建立视线旋转坐标系并设计APN制导律,在传统比例导引的基础上增加了对视线方向上速度的设计,使追踪航天器以可控的速度和较高的精度接近目标航天器。对多种共面绕飞构型进行了设计,并推导了各个绕飞构型的轨迹函数。为了保证更好的观测效果,以相对距离变化量和能量消耗的角度对各个构型的性能进行对比,最后各个绕飞构型的性能进行总结。在逼近段,考虑到目标航天器可能发生转动,设计了合理的逼近方案。建立了相对位置和姿态控制模型,在此基础上设计了自抗扰控制律,通过控制加速度和角加速度,使追踪航天器在不断接近目标航天器抓捕点的同时,对接端口始终指向目标航天器。最后通过仿真对设计的逼近方案进行验证。更多还原

【Abstract】 The rendezvous and docking technology of non-cooperative targets has great potential value in space environment cleaning,improving the efficiency of satellite utilization and military strategy.In recent years,it has been concerned and studied by a large number of scholars.In this paper,the approach orbit design and attitude control technology of non-cooperative target in space are studied.The design method of each segment is given and the corresponding calculation examples and simulation analysis are given.Firstly,the relative coordinate system and the corresponding transformation relationship are defined,the flight dynamics model and the perturbation model are established,and the relative orbit dynamics model of spacecraft is derived,which provides the theoretical basis for the later algorithm design.In the short-range guidance section,considering the inaccurate measurement of non-cooperative target orbit information,the short-range guidance section is divided into two stages according to the relative distance.When the relative distance is relatively long,the pulse guidance based on C-W state equation is used for preliminary approach,and the design method of double pulse and multi pulse orbit transfer is derived and given;when the relative distance is relatively short,the line of sight guidance is used,the line of sight rotation coordinate system is established and the APN guidance rate is designed,and the design of the speed in the line of sight direction is added on the basis of the traditional proportional guidance,so as to track the spacecraft Approach the target spacecraft with controllable speed and high precision.Several kinds of coplanar flying around configurations are designed,and the trajectory functions of each flying around configuration are derived.In order to ensure better observation effect,the performance of each configuration is compared from the angle of relative distance change and energy consumption.Finally,the performance of each flying around configuration is summarized.In the approach phase,considering the possible rotation of the target spacecraft,a reasonable approach scheme is designed.Based on the relative position and attitude control model,the auto disturbance rejection control rate is designed.By controlling the moment and overload,the tracking spacecraft can keep approaching the capture point of the target spacecraft,while the docking port always points to the capture point direction of the target spacecraft(the docking port axis).Finally,the approximation scheme is verified by simulation.更多还原